N381QS

Part: RIB — CRACKED (ZONE 300) · airframe 13,650 hrs · 9,092 cycles

LH ELEVATOR WEDGES PANEL INBOARD ATTACH RIB IS CRACK. ACCOMPLISHED LH HORIZONTAL STABILIZER INBOARD RIB DAMAGE REPAIR IAW TEXTRON AVIATION REPAIR MEMO DQ41081M1.

Part: BATTERY — INOPERATIVE (ZONE 100) · airframe 13,649 hrs · 9,091 cycles

EMERGENCY LIGHTING: ALL THE EMERGENCY LIGHTS ASSOCIATED WITH NUMBER 4 BATTERY PACK ARE INOP. GAINED ACCESS TO AND REMOVED AND REPLACED #4 EMERGENCY LIGHT BATTERY. CHARGED BATTERY AS CHECKS GOOD.CLOSED UP ALL. ACCESS. IAW CE680 MM 33-50-10

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 13,542 hrs · 9,021 cycles

ONCE DESCENDING PRESSURIZATION WILL RAPIDLY SPIKE UP TO 1000FT/MIN THEN STABILIZE CAUSING DISCOMFORT FOR PASSENGERS. CONTINUING THE DESCENT PRESSURIZATION WILL SPORADICALLY INCREASE AND DECREASE BETWEEN 500FT/MIN.

Part: BATTERY PACK — DISCHARGED · airframe 13,472 hrs · 8,980 cycles

FOUR LIGHTS OF THE EMERGENCY LIGHTING SYSTEM FAIL TO ILLUMINATE. THE LAV OVERHEAD LIGHT, THE TABLE OVERHEAD LIGHTS OF SEATS 5 AND 9, AND THE EMERGENCY EXIT FORWARD WING LIGHT.

Part: ROD — BROKEN (ZONE 800) · airframe 13,472 hrs · 8,980 cycles

MAIN DOOR: WHILE CLOSING THE DOOR SOME MINOR BINDING WAS ENCOUNTERED. THE DOOR WOULD NOT EXTEND FREELY ON OPENING AND FORCE WAS REQUIRED TO OVERCOME THE BINDING. THE RIGHT BOTTOM STRUT SEGMENT DISPLAYS BENDING. REMOVED AND REPLACED MED AFT TELESCOPING ROD IA W CE680 AMM 52-10-30. ADJUSTED CABIN DOOR COUNTER BALANCE SYSTEM AND PERFORMED OPS CK IN REF WITH CE680 AMM 52-10-5- OPS CHECK GOOD.

Part: LIGHT — DISCONNECTED · airframe 12,949 hrs · 8,638 cycles

LAV EXIT SIGN/LIGHT: EMERGENCY EXIT SIGN ON BASE OF LAVATORY SEAT DOES NOT ILLUMINATE. //SIGNOFF/ FOUND EMERGENCY EXIT SIGN ON BASE OF LAVATORY SEAT TO BE DISCONNECTED, RECONNECTED AS REQUIRED AND OPS CHECK GOOD. NO DEFECTS NOTED.

Part: NONE — NONE · airframe 12,943 hrs · 8,633 cycles

CABIN ODOR: AT 41,000FT, APU OFF, ANY POWER SETTING, ODOR FROM BOTH BLEEDS. CREW EYES AND THROAT STINGING, HEADACHE. RH ENGINE REMOVED AND REPLACED. ENG CAL AND LEAK CHECKS GOOD NO DEFECTS NOTED.

Part: SIGN — INOPERATIVE (EMERGENCY LIGHTS) · airframe 12,543 hrs · 8,370 cycles

MAIN EXIT SIGN/LIGHT: EMERGENCY LIGHT INOP. REMOVED FAILED SPLICE FROM AFT LH BULKHEAD EMERGENCY EXIT SIGN AND REPLACED WITH NEW UNIT. IAW CE-680 SPM 20-30-25. OPS CHECK GOOD. IAW CE-680 AMM 33-50-00.

Part: DRAG ANGLE — CORRODED (LT WING) · airframe 12,118 hrs · 8,089 cycles

LEFT WING AFT DRAG ANGLE HAS 2 AREAS OF VERIFIED CORROSION ALONG OUTBOARD EDGE AND 8 AREAS OF VERIFIED CORROSION ON MIDDLE DRAG ANGLE OUTBOARD EDGE. RIGHT UPPER WING AFT DRAG ANGLE HAS 1 AREA OF VERIFIED CORROSION ALONG OUTBOARD EDGE AND 7 AREAS OF VERIFIED CORROSION ON MIDDLE DRAG ANGLE OUTBD EDGE. REPAIRED LT AND RT WING SIDE DRAG ANGLE CORROSION, PER TEXTRON AVIATION FIELD REPAIR: FR-680-0097-8375 REV -, TITLED "FIELD REPAIR-CORROSION, WING, UPPER SKINS, LT/RT WS 37, APPROVED ON FAA FORM 8100-9 DATED 17 SEPT 2020.

Part: SPLICE STRAP — DEBONDED (HORIZ STAB) · airframe 11,334 hrs · 7,543 cycles

HORIZONTAL STABILIZER LEFT SIDE LOWER SKIN SPLICE STRAP DE-BONDED. ACCOMPLISHED ENGINEERING LETTER DQ22440M1 DATED JULY 25, 2019; 680-0097 HORIZONTAL STABILIZER LEFT SIDE LOWER SKIN SPLICE STRAP DE-BONDED.

Part: TORQUE TUBE — CRACKED (RUDDER) · airframe 10,264 hrs · 6,789 cycles

CRACKED RUDDER TORQUE TUBE FROM RUDDER. REPLACED THE RUDDER TORQUE TUBE IAW SRM 51-40-03, 51-40-06, 51-60-03, 55-40-09, AND MM 20-40-20.

Part: SKIN — CRACKED (RUDDER)

CRACK ON LOWER RUDDER SKIN ON RT SIDE EXTENDING FROM BOTTOM OF RUDDER ONE INCH INTO A RIVET. REPAIRED THE RUDDER SKIN IAW ERO-897400, REV IR. PERFORMED EDDY CURRENT ON CUTOUT AREA. INSPECTION REVEALED NO CRACK INDICATIONS.

Part: SWITCH — OUT OF ADJUST (DOOR) · airframe 8,825 hrs · 5,849 cycles

AT 500' ON CLIMBOUT AMBER, NOSE DOOR OPEN RT, CAS ILLUMINATED. WHEN TURNING FINAL AND AT A SLOWER SPEED IT EXTINGUISHED. ADJUSTED BOTH RT DOOR SWITCHES AND OPS CHECKED GOOD IAW MM 52-40-00.

Part: FIRE LOOP — FAILED (RT NACELLE) · airframe 6,988 hrs · 4,647 cycles

RECEIVED AN ENGINE FIRE DETECTOR FAIL ON RT CAS. R & R RT ENG OUTER FIRE LOOP. PERFORMED OPERATIONS CHECK, OPERATIONS CHECKED GOOD AT THIS TIME IAW MM 26-10-01.

Part: FITTING — CORRODED (WING) · airframe 6,060 hrs · 4,043 cycles

CORRODED WING RIB FITTINGS. REPAIRED IAW REPAIR DEF S-680-ATA57/01RD

Part: HEAT EXCHANGER — CRACKED (ZONE 400) · airframe 5,316 hrs

DURING A SCHEDULED INSPECTION, HEAT EXCHANGER SIDE PLATE HAD A .35" LONG CRACK AND THE OPPOSITE SIDE WAS ALSO CRACKED IN ONE CORNER. PERFORMED A LEAK DOWN TEST OF THE DEFECTIVE HEAT EXCHANGER AND FOUND THAT THE CRACK EXTENDED INTO THE INTERNAL PORTION OF THE EXCHANGER IN THE COOLING FIN AREAS.

Part: HEAT EXCHANGER — CRACKED (ZONE 400) · airframe 5,316 hrs

DURING A SCHEDULED INSPECTION, NOTICED HEAT EXCHANGER SIDE PLATE HAD 3. 35" LONG CRACK AND THE OPPOSITE SIDE WAS ALSO CRACKED IN ONE CORNER. WE PERFORMED A LEAK DOWN TEST OF THE DEFECTIVE HEAT EXCHANGER AND FOUND THAT THE CRACK EXTENDED INTO THE INTERNAL PORTION OF THE EXCHANGER IN THE COOLING FIN AREAS.

Part: UPLOCK — OUT OF ADJUST (LANDING GEAR) · airframe 4,541 hrs · 3,002 cycles

LANDING GEAR UNLOCK ANNUNCIATOR ILLUMINATED AT FL430 AND REMAINED ON UNTIL GEAR HANDLE WAS SELECTED TO THE DOWN POSITION. PERFORMED SEVERAL LANDING GEAR RETRACTIONS AND EXTENSIONS. NO DEFECTS NOTED. FROZE ALL 3 MLG UPLOCK SWITCHES. OPERATED MLG. NO FAULTS NOTED. CHECKED UPLOCK SWITCHES FOR RIGGING. FOUND NOSE UPLOCK AND LT MLG UPLOCK SLIGHTLY OUT OF RIG. ADJUSTED BOTH SWITCHES BY 1 TURN OF THE JAM NUT. RECHECKED UPLOCK RIGGING. OPS CHECK GOOD. WORK DONE IAW MM 32-60-00. ELECTRICITY CHECK ALL 3 UPLOCK SWITCH FOR HIGH RESISTANCE OR LOOSE CONNECTIONS. NO FAULTS FOUND. INSPECTED LANDING EMERGENCY RELEASE SYS. NO DEFECTS NOTED.

Part: STRUT — DISCHARGED (NLG) · airframe 3,535 hrs · 2,327 cycles

LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. WOW MISCOMPARE CAS MSG ILLUMINATED. GEAR HANDLE WOULD NOT MOVE. CHECKED SQUAT SWITCH RIGGING ON ALL 3 GEARS. NO DEFECTS NOTED, T-SHOT, FOUND THAT NLG STRUT COULD BE COMPRESSED +/- 1" WHICH WOULD DISENGAGE NLG SQUAT SWITCH, CHECKED NOSE STRUT PRESSURE & FOUND LWR CHAMBER TO HAVE VERY LITTLE AIR PRESSURE. NEED TO PERFORM COMPLETE NOSE STRUT SERVICE. SERVICED UPPER AND LOWER CHAMBERS ON NLG STRUT, OPS CHECK OF GEAR GOOD IAW MM 32-20-00 & MM 32-00-00, DOWNJACKED ACFT.

Part: VALVE — LEAKING (NLG) · airframe 3,341 hrs · 2,208 cycles

GEAR WOULD NOT RETRACT (HANDLE LOCKED OUT) WOW MISCOMPARE. VISUALLY INSPECTED SQUAT SWITCHES. OPS CHECKED ALL SQUAT SWITCHES AND VERIFIED INPU IN OT IAW PCB JACKED ACFT AND PERFORMED GEAR SWING. NO DISPREANCIES FOUND. CHECKED SERVICE OF NOSE STRUT, FOUND UPPER CHAMBER PEOPERLY SERVICED BUT LOWER CHAMBER AT ZERO PSI CW COMPLETE STRUT SERVICE AND REPLACED IAW STRUT SERVICING VALVE IAW MM, CHAP 32-20-00, REV 17. LEAK AND OPS CHECK GOOD.

Part: OIL SYSTEM — OVERSERVICED (APU) · airframe 3,288 hrs · 2,173 cycles

AFTER LANDING AND WITHIN 3-5 MINS OF STARTING APU AND SELECTING THE BLEED AIR "ON", THE CABIN FILLED WITH SMOKE AND AN ODOR OF OIL. FOUND APU OIL OVER SERVICED. OIL COMING FROM GEAR CASE VENT TUBE. REMOVED 56 CC OF OIL. SERVICED OIL IAW RE-100CS, & MM 49-20-00. RAN APU WITH BLEED AIR TWICE. NO OIL LEAKS, SMOKE, OR OIL ODOR NOTED.

Part: CONTROLLER — MALFUNCTIONED (HORIZ STAB TRIM) · airframe 2,295 hrs · 1,515 cycles

PRIMARY PITCH TRIM FAIL - POSSIBLY RAN AWAY BUT CAUGHT BY THE CREW. SECONDARY TRIM WORKED AS NEEDED. TOOK BOTH CREW MEMBERS TO INITIALLY LEVEL THE PLANE. LANDED WITH NO OTHER EVENT. CDMS LISTED ACTUATOR OR CONTROLLER AS FAULT. TESTED OTHER COMPONENTS OF SYSTEM, NO FAULTS FOUND. OPS CHECK OF SYSTEM AT THIS TIME NORMAL. RECOMMEND REPLACEMENT OF CONTOLLER. REMOVED AND REPLACED STAB ACTUATOR CONTROLLER WITH OVERHAULED UNIT. OPERATIONAL CHECK NORMAL. WORK DONE IAW MM 27-40-00.

Part: DISPLAY — SHORTED (COCKPIT) · airframe 2,162 hrs · 1,428 cycles

APPROX 1.5 HR AFTER TAKEOFF THE LT MCDU (FMS CDU) BECAME INOP (BLANK SCREEN / NO RED X) LT MCDU CB WAS NOT TRIPPED. APPROX 5-10 MINS LATER STARTED SMELLING SLIGHT ELECTRICAL ODOR WHICH GREW INTO A STRONG ELECTRICAL ODOR WITHIN 5 MIN. REMOVED AND REPLACED MFD CONTROL DISPLAY UNIT.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT)

AFTER TAKEOFF INFLIGHT ANYTIME PITCH TRIM IS ACTIVATED EITHER NOSE UP OR DOWN, AMBER "AP STAB TRIM INOP" & AMBER "PRIMARY STAB TRIM FAIL" & CYAN "AP FAIL A & B" CAS MESSAGES DISPLAYED. PERFORMED OPS CK OF THE PITCH TRIM SWITCHING FOR SEVERAL HOURS WITH ACFT. IN AIRMODE AND AT ALTITUDE (SK-10K FT. AND 150- 200 KTS. COULD NOT DUPLICATE FAULT. TRIED DIFFERENT SCENARIOS, BUT NO FAULTS NOTED. AVP SYSTEM OP.S CKD. GOOD DURING THIS TESTING IAW MM 27-40-00.

Part: CABIN PRESSURE — MALFUNCTIONED · airframe 1,204 hrs · 791 cycles

ON CLIMBOUT, AC PRESSURIZED UNTIL 9.3 PSI SWITCHED TO MANUAL AND WAS ABLE TO CONTROL PRESSURIZATION, SWITCHED BACK TO AUTO FOR THE DESCENT AND APPEARED TO OPERATE NORMALLY IN DESCENT. OPERATIONALLY CHECKED PRESSURIZATION SYS IAW MM CH 21-30-00, NO DISCREPANCIES NOTED. OPS CHECKS GOOD.

Part: HEATER — MALFUNCTIONED (PITOT LINE) · airframe 1,182 hrs · 773 cycles

AMBER PITOT STATIC COLD R CAME ON DURING T/O ROLL. CYCLED SEVERAL TIMES, INTERMITTENT THEREAFTER. TROUBLESHOT PITOT STATIC SYS AND FOUND SYS TO WORK NORMAL SEVERAL TIMES. COMPLIED WITH PITOT STATIC AND STANDBY HEATER CHECK IAW MM CH 34-11-00. INSPECTED RT PITOT HEATER WIRING CONNECTOR, FOUND TO BE GOOD.

Part: UNKNOWN — UNKNOWN (RUDDER TRIM) · airframe 594 hrs · 381 cycles

AIRCRAFT REQUIRES 2/3 SCALE LT RUDDER TRIM TO MAINTAIN COORDINATED FLIGHT. [07-09-07] RUDDER SKIN DAMAGED AT UPPER, MIDDLE AND LOWER RUDDER HINGE AREA. REMOVED RUDDER AND REPLACED WITH REPAIRED UNIT FROM CESSNA ICT RS CNQR918C PER 680 MM CH 55-40-00. OPERATIONAL AND TRAVEL CHECK OF RUDDER AND RUDDER TRIM GOOD.

Part: COUPLER — INOPERATIVE (SPOILERS) · airframe 593 hrs · 379 cycles

ON TAKEOFF, WE RECEIVED A (NO TO CAS) MESSAGE THAT WAS CAUSED BY THE SPOILERS. REMOVED AND REPLACED RT SPEED BRAKE COUPLER. PERFORMED ELECTRONIC RIGGING IAW MM 27-60-00. OPS CHECK GOOD.

Part: TRANSFER PUMP — INOPERATIVE (FUEL SYSTEM) · airframe 193 hrs · 124 cycles

CROSS FEED (ON) IN AIR (2 OCCASIONS). CROSS FEED VALVES FAILED TO OPEN, BOTH FUEL BOOST PUMPS (LOW PRESS) CAME ON. EICAS MESSAGES APPROPRIATE AMBER FUEL PRESS LOW L-R ON. TROUBLESHOT PROBLEM TO LT BOOST PUMP. REMOVED FAILED BOOST PUMP AND INSTALLED A NEW BOOST PUMP. OPERATION CHECKS GOOD. LEAK CHECKS GOOD. WORK PERFORMED IAW CH 28-20-00 OF THE CES 680 MM.